CN101446236A - Lubricating and cooling device of rotor bearing of jet engine of microminiature turbine - Google Patents
Lubricating and cooling device of rotor bearing of jet engine of microminiature turbine Download PDFInfo
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- CN101446236A CN101446236A CNA2008102473606A CN200810247360A CN101446236A CN 101446236 A CN101446236 A CN 101446236A CN A2008102473606 A CNA2008102473606 A CN A2008102473606A CN 200810247360 A CN200810247360 A CN 200810247360A CN 101446236 A CN101446236 A CN 101446236A
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Abstract
本发明公开了一种微小型涡轮喷气发动机转子轴承润滑冷却装置，包括燃油管路、滑油管路和节流器。在航空煤油中按一定比例添加润滑油组成混合油，混合油经过油泵加压，进入燃油管路和滑油管路，燃油管路的混合油直接进入燃烧室进行燃烧，滑油管路的混合油进入前后两个轴承腔对轴承进行润滑，完成润滑后滑油不再循环，从前轴承进入的滑油可进入燃烧室进行燃烧，从后轴承进入的滑油一部分在涡轮处燃烧，未燃烧的部分随燃气排出发动机。本发明只需要一个油泵给混合油加压，转子轴承腔不需要各种油气封严措施，滑油管路出口处不需要密封器件，使发动机结构简单，质量轻，增加了发动机的有效载荷。
The invention discloses a lubricating and cooling device for rotor bearings of a miniature turbojet engine, which comprises a fuel pipeline, a lubricating oil pipeline and a restrictor. Lubricating oil is added to aviation kerosene in a certain proportion to form a mixed oil. The mixed oil is pressurized by the oil pump and enters the fuel pipeline and lubricating oil pipeline. The mixed oil in the fuel pipeline directly enters the combustion chamber for combustion, and the mixed oil in the lubricating oil pipeline enters the The two bearing chambers at the front and rear lubricate the bearings. After the lubrication is completed, the lubricating oil will no longer circulate. The lubricating oil entering from the front bearing can enter the combustion chamber for combustion. Gas exits the engine. The invention only needs one oil pump to pressurize the mixed oil, the rotor bearing cavity does not need various oil-gas sealing measures, and the lubricating oil pipeline outlet does not need sealing devices, so that the engine structure is simple, the weight is light, and the effective load of the engine is increased.
Description
Technical field
The present invention relates to engine lubrication cooling technology field, be specifically related to a kind of lubricating and cooling device of rotor bearing of jet engine of microminiature turbine.
Background technique
Jet engine of microminiature turbine has compact structure, lightweight characteristics, and this has determined the lubricated of its rotor-support-foundation system must adopt the light weight design.Rotor-support-foundation system comprises gas compressor, engine shaft, turbine, bearing and bearing sleeve.The bearing of rotor adopts angular contact ball bearing to bear the axial force of motor.This angular contact ball bearing adopts that grease lubrication is the highest can be operated in 110,000 commentaries on classics, adopt that oil lubrication is the highest can be operated in 160,000 commentaries on classics, the maximum speed of jet engine of microminiature turbine changes 120,000, consider the reliability of rotor-support-foundation system work, on jet engine of microminiature turbine, adopt the oil lubrication mode usually.
The lubricated cooling problem of rotor bearing is the emphasis of aviation turbojet engine always, also is the focus that people pay close attention to.Traditional way is that the lubricating oil with tape loop pressure is ejected on the bearing of running, lubricating bearings on the one hand, and the circuit lubricating oil also can be taken away the frictional heat that produces in the bearing operation on the other hand.But for small-sized and miniature aeroengine, if working pressure oil lubrication scheme, then the same with big-block engine lubricating oil tank, lubricating oil pump, flow control mechanism, oily filter, oil separator, cooling unit, the turnover oil pipes etc. of needing, this need increase a large amount of annexes.Because the rotating speed of miniature aeroengine is very high, very rotating speed reaches into big retarding, the rotating speed of dump pump requirement than just making, this certainly will also increase the reducer structure complexity, cause retarder and whole lubricating and cooling shared volume and weight in whole motor all very big simultaneously, thrust weight ratio reduces.Therefore adopt this method can bring a lot of problems, can not look after small-sized and particularity tiny engine.
Summary of the invention
The objective of the invention is provides a kind of simple in structure for jet engine of microminiature turbine, the lubricating and cooling device of rotor bearing that weight is little, adopt made of light design, in aviation kerosine, add lubricant oil by a certain percentage and form miscella, miscella is through the oil pump pressurization, enter fuel pipe and lube pipe, the miscella of fuel pipe directly enters the firing chamber and burns, the miscella of lube pipe enters former and later two bearing bores bearing is lubricated, finish the not recirculation of lubricating oil of lubricated back, the lubricating oil that enters from fore bearing can enter the firing chamber and burn, burn at turbine from the lubricating oil part that rear bearing enters, unburned part is discharged motor with combustion gas.
A kind of lubricating and cooling device of rotor bearing of jet engine of microminiature turbine of the present invention comprises fuel pipe, lube pipe and flow controller.
Aviation kerosine mixes the formation miscella with bearing oil according to required ratio in fuel tank, miscella is contained in the fuel tank to be pumped to cooling unit by oil pump provides cooling medium.
Fuel pipe is made up of first section pipeline and second section pipeline connection, and second section pipeline is circular pipeline.Second section pipeline below is distributed with several fuel outlets.Lube pipe has two outlets, is respectively outlet A and outlet B, and the miscella that described outlet A and outlet B flow out enters the gas compressor step bearing respectively and is lubricated with the turbine end bearing and cools off.The fuel pipe inlet is connected by three-way valve with the lube pipe inlet, and another interface of three-way valve connects quick plug, and the quick plug that connects on the three-way valve connects oil pump.
Be respectively equipped with the consumption of flow controller control lubricating oil near lube pipe outlet A, the outlet B.
Lubrication hole A is offered in position at the corresponding gas compressor step bearing of the radial-axial Diffuser sidewall of motor, and lubrication hole B is offered in the position of the corresponding turbine end bearing of rotor axle sleeve.On the lubricating oil dish of motor, offer the lubricating oil oil outlet.The fuel pipe inlet is separately fixed in the cover dish hole of motor radial-axial Diffuser with the lube pipe inlet.Above cover dish hole, seal with O type circle.The outlet A of lube pipe is fixed among the lubrication hole A, and outlet B is fixed among the lubrication hole B.The miscella that outlet A flows out at first enters in the lubricating oil dish in the rotor axle sleeve, enter into the space at gas compressor step bearing rear by the lubricating oil oil outlet on the lubricating oil dish, moving forward into the gas compressor step bearing under the air pressure effect of centrifugal-flow compressor impeller is lubricated it and cools off, last miscella is by the space between centrifugal-flow compressor impeller and the radial-axial Diffuser, and the water conservancy diversion that passes through the radial-axial Diffuser again enters into the firing chamber and burns.The miscella that outlet B flows out directly sprays to the ball of turbine end bearing, it is lubricated and cools off, afterwards under the inside and outside differential pressure effect of rotor axle sleeve, behind rotor axle sleeve and turbine gap between the two, flow to turbine blade, the part burning of can being heated at the turbine place, unburned part is discharged motor with combustion gas.
The invention has the advantages that:
(1) simple in structure, alleviate engine weight.Aviation kerosine and lubricant oil are mixed in proportion, form miscella, only need an oil pump to pressurize to miscella, reduced annex, the rotor bearing chamber no longer needs the measure of obturaging of various oil gas in addition, has reduced the castor tooth of obturaging, the parts such as ring, linkage structure of obturaging;
(2) lube pipe simplicity of design adopts and inserts design, needn't consider to be tightly connected in the outlet port;
(3) arrange during flow controller is in order to the control miscella consumption in two outlet ports of lube pipe as lubricant oil;
(4) miscella that plays lubricated cooling action does not circulate, and has reduced equipment such as cooling unit, turnover oil pipe, makes engine structure simple, and light weight has increased the useful load of motor.
Description of drawings
Fig. 1 is the structural representation of a kind of lubricating and cooling device of rotor bearing of jet engine of microminiature turbine of the present invention;
Fig. 2 is the structural representation after the present invention assembles core engine;
Fig. 3 is the radial-axial Diffuser structural representation of motor;
Fig. 4 is the rotor axle sleeve structural representation of motor;
Fig. 5 is the lubricating oil dish structural representation of motor.
Among the figure: the 1-fuel pipe; The 2-lube pipe; The 3-flow controller; The 4-oil pump; 5-gas compressor step bearing; 6-turbine end bearing; 7 three-way valve; The 8-quick plug; 9-radial-axial Diffuser; 10-lubrication hole A; The 11-rotor axle sleeve; 12-lubrication hole B; 13-lubricating oil dish; 14-lubricating oil oil outlet; 15-cover dish hole; 16-centrifugal-flow compressor impeller; The 17-firing chamber; The 18-turbine; 101-fuel pipe inlet; First section pipeline of 102-; Second section pipeline of 103-; The 104-fuel outlet; 201-lube pipe inlet; 202-exports A; 203-exports B.
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
The present invention is a kind of lubricating and cooling device of rotor bearing of jet engine of microminiature turbine, as shown in Figure 1, comprises fuel pipe 1, lube pipe 2 and flow controller 3.
Aviation kerosine mixes the formation miscella with bearing oil according to required ratio in fuel tank, miscella is contained in the fuel tank to be pumped to cooling unit by oil pump 4 provides cooling medium.Provide lubricant oil and fuel oil to motor simultaneously by an oil pump 4, alleviated the weight of motor.
As shown in Figure 1, fuel pipe 1 is communicated with by first section pipeline 102 and second section pipeline 103 and forms, and second section pipeline 103 is circular pipeline.Second section pipeline 103 below is distributed with several fuel outlets 104, and miscella enters from fuel pipe inlet 101, discharges from fuel outlet 104, burns, for motor provides power.As Fig. 1, Fig. 2, lube pipe 2 has two outlets, is respectively outlet A202 and outlet B203, and the miscella that described outlet A202 and outlet B203 flow out enters gas compressor step bearing 5 respectively and is lubricated with turbine end bearing 6 and cools off.Fuel pipe 1 inlet 101 and lube pipe 2 inlets 201 are connected three-way valve 7 another interfaces connection quick plugs 8, quick plug 8 connection oil pumps 4 by three-way valve 7.
In the time of work, oil pump 4 is to the miscella pressurization, and miscella enters three-way valve 7 back shuntings, and most of miscella enters by fuel outlet 104 discharges by fuel pipe 1 and burns, for motor provides power, small part is lubricated bearing as lubricant oil by lube pipe 2 and cools off.Be respectively equipped with flow controller 3 near the outlet A202 of lube pipe 2, the outlet B203, in order to the consumption of control lubricating oil.The rotating speed of lube use rate and motor is one to one, rotating speed height then fuel consumption increases, therefore the oil flow of lube pipe 2 all is that increase with rotating speed increases, for the increase of rotating speed, described lubricating and cooling device of rotor bearing of jet engine of microminiature turbine enters the oil flow of bearing by flow controller 3 controls.
As shown in Figure 3, offer lubrication hole A10 in the position of the corresponding gas compressor step bearing 5 of radial-axial Diffuser 9 sidewalls of motor, as shown in Figure 4, lubrication hole B12 is offered in the position of rotor axle sleeve 11 corresponding turbine end bearings 6.As shown in Figure 5, on the lubricating oil dish 13 of motor, offer lubricating oil oil outlet 14, make miscella enter gas compressor step bearing 5 from lubricating oil dish 13.Fuel pipe 1 inlet 101 is separately fixed in the cover dish hole 15 of motor radial-axial Diffuser 9, as Fig. 2, shown in Figure 3 with lube pipe 2 inlets 201.Above cover dish hole 15, seal with O type circle.As Fig. 2, shown in Figure 4, the outlet A202 of lube pipe 2 is fixed among the lubrication hole A10, and outlet B203 is fixed among the lubrication hole B12.Lube pipe 2 all adopts the simple design of inserting, and does not consider to be tightly connected, and saves air locking, alleviates the weight of motor.The miscella that outlet A202 flows out at first enters in the lubricating oil dish 13 in the rotor axle sleeve 11, enter into the space at gas compressor step bearing 5 rears by the lubricating oil oil outlet 14 on the lubricating oil dish 13, moving forward into gas compressor step bearing 5 under the air pressure effect of centrifugal-flow compressor impeller 16 is lubricated it and cools off, last miscella is by the space between centrifugal-flow compressor impeller 16 and the radial-axial Diffuser 9, and the water conservancy diversion that passes through radial-axial Diffuser 9 again enters into firing chamber 17 and burns.The miscella that outlet B203 flows out directly sprays to the ball of turbine end bearing 6, it is lubricated and cools off, afterwards under the inside and outside differential pressure effect of rotor axle sleeve 11, behind rotor axle sleeve 11 and turbine 18 gap between the two, flow to turbine blade, the part burning of can being heated at turbine 18 places, unburned part is discharged motor with combustion gas.
Claims (5)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008102473606A CN101446236A (en) | 2008-12-30 | 2008-12-30 | Lubricating and cooling device of rotor bearing of jet engine of microminiature turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008102473606A CN101446236A (en) | 2008-12-30 | 2008-12-30 | Lubricating and cooling device of rotor bearing of jet engine of microminiature turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101446236A true CN101446236A (en) | 2009-06-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2008102473606A Pending CN101446236A (en) | 2008-12-30 | 2008-12-30 | Lubricating and cooling device of rotor bearing of jet engine of microminiature turbine |
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| CN (1) | CN101446236A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102425472A (en) * | 2011-10-19 | 2012-04-25 | 中国南方航空工业(集团)有限公司 | Triangular rotor engine lubricating device and triangular rotor engine with same |
| CN103362650A (en) * | 2012-04-01 | 2013-10-23 | 中航商用航空发动机有限责任公司 | Cooling system and method of aero-engine |
| CN105937448A (en) * | 2016-07-08 | 2016-09-14 | 中国科学院工程热物理研究所 | Integral bearing support structure |
| CN107246324A (en) * | 2017-03-02 | 2017-10-13 | 蔡肃民 | A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement |
| CN108612588A (en) * | 2018-04-18 | 2018-10-02 | 常州环能涡轮动力股份有限公司 | Miniature aviation whirlpool axis drive system |
| CN111963484A (en) * | 2020-08-12 | 2020-11-20 | 四川航天中天动力装备有限责任公司 | High-integration-level diffuser structure for small turbine engine |
| CN112483415A (en) * | 2020-11-13 | 2021-03-12 | 西安航天动力研究所 | Liquid rocket engine low-temperature turbine pump based on integrated cylindrical supporting seat |
-
2008
- 2008-12-30 CN CNA2008102473606A patent/CN101446236A/en active Pending
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102425472A (en) * | 2011-10-19 | 2012-04-25 | 中国南方航空工业(集团)有限公司 | Triangular rotor engine lubricating device and triangular rotor engine with same |
| CN103362650A (en) * | 2012-04-01 | 2013-10-23 | 中航商用航空发动机有限责任公司 | Cooling system and method of aero-engine |
| CN103362650B (en) * | 2012-04-01 | 2016-03-30 | 中航商用航空发动机有限责任公司 | The cooling system of aeroengine and method thereof |
| CN105937448A (en) * | 2016-07-08 | 2016-09-14 | 中国科学院工程热物理研究所 | Integral bearing support structure |
| CN105937448B (en) * | 2016-07-08 | 2017-06-20 | 中国科学院工程热物理研究所 | A kind of integrated bearing seat structure |
| CN107246324A (en) * | 2017-03-02 | 2017-10-13 | 蔡肃民 | A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement |
| CN107246324B (en) * | 2017-03-02 | 2024-01-05 | 蔡肃民 | Vertical air-borrowing high-pressure cooling lubrication bearing structure of miniature turbojet engine |
| CN108612588A (en) * | 2018-04-18 | 2018-10-02 | 常州环能涡轮动力股份有限公司 | Miniature aviation whirlpool axis drive system |
| CN108612588B (en) * | 2018-04-18 | 2024-03-22 | 常州环能涡轮动力股份有限公司 | Miniature aviation vortex shaft driving system |
| CN111963484A (en) * | 2020-08-12 | 2020-11-20 | 四川航天中天动力装备有限责任公司 | High-integration-level diffuser structure for small turbine engine |
| CN112483415A (en) * | 2020-11-13 | 2021-03-12 | 西安航天动力研究所 | Liquid rocket engine low-temperature turbine pump based on integrated cylindrical supporting seat |
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Application publication date: 20090603 |